Tests of 12-ft span wing at Mach numbers up to 0.69; max lift coefficient varied with Mach number and was affected by sharpness of leading edge at higher Mach numbers; formation of extensive local supersonic flow regions caused center of pressure to move forward at high angles of attack and high Mach numbers.


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    Title :

    Effects of compressibility on lift, pressure, and load characteristics of tapered wing of NACA 66-series airfoil sections


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1948


    Size :

    59 pages


    Remarks:

    Bibliography


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :